Apparatus, System, and Method for Inspecting a Component

This specification is based upon and claims the benefit of priority from United Kingdom patent application number GB 2412431.5 filed on August 23, 2024, the entire contents of which is incorporated herein by reference.

This disclosure relates to an apparatus, a system, and a method for inspecting a gas turbine engine component.

Many components, such as heatshields, liners, tiles, and turbine blades of a gas turbine engine may be subjected to high thermal loads for prolonged periods of time. Such components may include cooling apertures through which a cooling fluid may be directed to increase the usable life of the components.

The components may include complex designs of the cooling apertures for improved cooling performance. Such complex designs of the cooling apertures may cause difficulties in inspection of the components, or more specifically, the cooling apertures of the components. For example, the cooling apertures may be designed to form a film of air along a hot-side surface of the components to improve cooling performance. However, the film of air may interfere with the inspection of the plurality of cooling apertures of the components.

In a first aspect, there is provided an apparatus for inspecting a gas turbine engine component having a plurality of cooling apertures. The apparatus includes a main body including a plurality of body apertures configured to at least partially align with the plurality of cooling apertures of the gas turbine engine component. Each body aperture from the plurality of body apertures extends through the main body. The apparatus further includes a seal connected or connectable to the main body. The seal is configured to engage with the gas turbine engine component. The seal includes a plurality of seal apertures corresponding to the plurality of body apertures. Each seal aperture from the plurality of seal apertures extends through the seal. The plurality of seal apertures is at least partially aligned with the plurality of body apertures of the main body, such that the plurality of seal apertures is disposed or disposable in fluid communication with the plurality of body apertures.

The apparatus may improve an inspection of the gas turbine engine component. Specifically, the apparatus may facilitate obtaining accurate and precise data associated with the plurality of cooling apertures of the gas turbine engine component. The apparatus may be suitable for use with gas turbine engine components having complex designs of the plurality of cooling apertures.

The apparatus may be arranged in a testing configuration with respect to the gas turbine engine component to carry out the inspection. In the testing configuration, the plurality of seal apertures is at least partially aligned with the plurality of cooling apertures, and the plurality of body apertures is at least partially aligned with the plurality of seal apertures, such that the plurality of body apertures is disposed in fluid communication with the plurality of cooling apertures of the gas turbine engine component.

In some embodiments, thermographic inspection may be carried out using the apparatus in the testing configuration by directing a flow of air through the plurality of cooling apertures of the gas turbine engine component, such that the air egresses from the plurality of body apertures of the main body. The main body and the seal may reduce or prevent formation of a cooling film (due to the flow of air) over a surface of the main body opposite to the seal. As a result, a segmented response from each cooling aperture may be obtained. In other words, the apparatus may allow obtaining discrete data associated with each cooling aperture of the gas turbine engine component. Additionally, the surface of the main body opposite to the seal and a plurality of aperture wall surfaces that define the plurality of body apertures may have predetermined and/or calibrated infrared properties to facilitate the thermographic inspection. It may be noted that the infrared properties of the surface of the main body opposite to the seal may be different from the infrared properties of the plurality of aperture wall surfaces. Furthermore, the plurality of body apertures may be optimised to compensate for parallax errors of a thermography device including a thermal imaging camera, thereby facilitating the thermographic inspection.

In some embodiments, the seal includes a first major seal surface and a second major seal surface disposed opposite to the first major seal surface. Each seal aperture extends from the first major seal surface to the second major seal surface. The first major seal surface is configured to engage with the gas turbine engine component. The second major seal surface is configured to engage with the main body.

In some embodiments, the main body includes a first major body surface and a second major body surface disposed opposite to the first major body surface. Each body aperture extends from the first major body surface to the second major body surface. The first major body surface is configured to engage with the second major seal surface.

In some embodiments, the main body includes a plurality of aperture wall surfaces extending from the first major body surface to the second major body surface and defining the plurality of body apertures. Each aperture wall surface from the plurality of aperture wall surfaces has a set of first predetermined infrared properties. The second major body surface has a set of second predetermined infrared properties different from the set of first predetermined infrared properties.

In some embodiments, the main body further includes a central portion. The plurality of body apertures is disposed on the central portion. The main body further includes a peripheral portion surrounding the central portion. The main body further includes at least one pair of coupling apertures spaced apart from each other and disposed on the peripheral portion. Each of the at least one pair of coupling apertures extends through the main body.

In some embodiments, the apparatus further includes an inspection fixture including a receiving portion configured to receive and retain the gas turbine engine component. The inspection fixture further includes a coupling portion surrounding the receiving portion. The inspection fixture further includes at least one pair of coupling features corresponding to the at least one pair of coupling apertures of the main body. The at least one pair of coupling features is disposed on the coupling portion.

In some embodiments, the apparatus further includes at least one pair of coupling elements configured to extend through the at least one pair of coupling apertures and couple with the at least one pair of coupling features to detachably couple the main body to the inspection fixture.

In some embodiments, the main body defines a plane and a normal to the plane. The plurality of body apertures includes a set of first body apertures aligned with the normal. The plurality of body apertures further includes a set of second body apertures obliquely inclined to the normal.

In some embodiments, the main body and the seal are integral.

40 60 In some embodiments, the seal includes a Shore A hardness fromto.

In some embodiments, each seal aperture has a first diameter. Each body aperture has a second diameter. The first diameter is greater than the second diameter.

In a second aspect, there is provided a system for inspecting a gas turbine engine component having a plurality of cooling apertures. The system includes an apparatus. The apparatus includes a main body including a plurality of body apertures configured to at least partially align with the plurality of cooling apertures of the gas turbine engine component. Each body aperture from the plurality of body apertures extends through the main body. The main body further includes a plurality of aperture wall surfaces defining the plurality of body apertures. Each aperture wall surface from the plurality of aperture wall surfaces defines a corresponding body aperture from the plurality of body apertures. The apparatus further includes a seal connected or connectable to the main body. The seal is configured to engage with the gas turbine engine component. The seal includes a plurality of seal apertures corresponding to the plurality of body apertures. Each seal aperture from the plurality of seal apertures extends through the seal. The plurality of seal apertures is at least partially aligned with the plurality of body apertures of the main body, such that the plurality of seal apertures is disposed or disposable in fluid communication with the plurality of body apertures. The system further includes a thermography device configured to obtain thermal image data associated with a surface of the main body opposite to the seal and the plurality of aperture wall surfaces.

The system may improve an inspection of the gas turbine engine component using the thermography device. Specifically, the system may facilitate obtaining accurate and precise data associated with the plurality of cooling apertures of the gas turbine engine component using the thermography device. The system may be suitable for use with gas turbine engine components having complex designs of the plurality of cooling apertures.

The apparatus of the system may be arranged in a testing configuration with respect to the gas turbine engine component to carry out the inspection. In the testing configuration, the plurality of seal apertures is at least partially aligned with the plurality of cooling apertures, and the plurality of body apertures is at least partially aligned with the plurality of seal apertures, such that the plurality of body apertures is disposed in fluid communication with the plurality of cooling apertures of the gas turbine engine component.

The system may be used to carry out thermographic inspection of the gas turbine engine component using the apparatus in the testing configuration by directing a flow of air through the plurality of cooling apertures of the gas turbine engine component, such that the air egresses from the plurality of body apertures of the main body. The main body and the seal may reduce or prevent formation of a cooling film (due to the flow of air) over a surface of the main body opposite to the seal. As a result, the thermography device may capture a segmented response from each cooling aperture. In other words, the system may facilitate the thermography device to capture discrete data associated with each cooling aperture of the gas turbine engine component. Additionally, the surface of the main body opposite to the seal and the plurality of aperture wall surfaces may have predetermined and/or calibrated infrared properties to facilitate the thermographic inspection by the thermography device. It may be noted that the infrared properties of the surface of the main body opposite to the seal may be different from the infrared properties of the plurality of aperture wall surfaces. Furthermore, the plurality of body apertures may be optimised to compensate for parallax errors of the thermography device.

In some embodiments, the seal includes a first major seal surface and a second major seal surface disposed opposite to the first major seal surface. Each seal aperture extends from the first major seal surface to the second major seal surface. The first major seal surface is configured to engage with the gas turbine engine component. The second major seal surface is configured to engage with the main body.

In some embodiments, the main body includes a first major body surface and a second major body surface disposed opposite to the first major body surface. Each body aperture extends from the first major body surface to the second major body surface. The first major body surface is configured to engage with the second major seal surface. The thermography device is configured to obtain the thermal image data associated with the second major body surface and the plurality of aperture wall surfaces.

In some embodiments, the main body includes a plurality of aperture wall surfaces extending from the first major body surface to the second major body surface and defining the plurality of body apertures. Each aperture wall surface from the plurality of aperture wall surfaces has a set of first predetermined infrared properties. The second major body surface has a set of second predetermined infrared properties different from the set of first predetermined infrared properties.

In some embodiments, the main body further includes a central portion. The plurality of body apertures is disposed on the central portion. a peripheral portion surrounding the central portion and at least one pair of coupling apertures spaced apart from each other and disposed on the peripheral portion. Each of the at least one pair of coupling apertures extends through the main body.

In some embodiments, the apparatus further includes an inspection fixture including a receiving portion configured to receive and retain the gas turbine engine component. The inspection fixture further includes a coupling portion surrounding the receiving portion. The inspection fixture further includes at least one pair of coupling features corresponding to the at least one pair of coupling apertures of the main body. The at least one pair of coupling features is disposed on the coupling portion.

In some embodiments, the apparatus further includes at least one pair of coupling elements configured to extend through the at least one pair of coupling apertures and couple with the at least one pair of coupling features to detachably couple the main body to the inspection fixture.

In some embodiments, the main body defines a plane and a normal to the plane. The plurality of body apertures includes a set of first body apertures aligned with the normal. The plurality of body apertures further includes a set of second body apertures obliquely inclined to the normal.

In some embodiments, the main body and the seal are integral.

40 60 In some embodiments, the seal includes a Shore A hardness fromto.

In some embodiments, each seal aperture has a first diameter. Each body aperture has a second diameter. The first diameter is greater than the second diameter.

In a third aspect, there is provided a method of inspecting a gas turbine engine component. The method includes providing a gas turbine engine component including a plurality of cooling apertures. The method further includes providing an apparatus. The apparatus includes a main body including a plurality of body apertures configured to at least partially align with the plurality of cooling apertures of the gas turbine engine component. Each body aperture from the plurality of body apertures extends through the main body. The main body further includes a plurality of aperture wall surfaces defining the plurality of body apertures. Each aperture wall surface from the plurality of aperture wall surfaces defines a corresponding body aperture from the plurality of body apertures. The apparatus further includes a seal including a plurality of seal apertures corresponding to the plurality of body apertures. Each seal aperture from the plurality of seal apertures extends through the seal. The plurality of seal apertures is at least partially aligned with the plurality of body apertures of the main body. The method further includes connecting the seal to the main body, such that the plurality of seal apertures is disposed in fluid communication with the plurality of body apertures. The method further includes engaging the gas turbine engine component with the seal of the apparatus, such that the plurality of cooling apertures aligns with the plurality of seal apertures. The method further includes directing a flow of air through the plurality of cooling apertures. The method further includes obtaining thermal image data associated with a surface of the main body opposite to the seal and the plurality of aperture wall surfaces. The method further includes determining an inspection parameter associated with the plurality of cooling apertures based on the thermal image data.

The method may improve an inspection of the gas turbine engine component. Specifically, the method may facilitate obtaining accurate and precise data associated with the plurality of cooling apertures of the gas turbine engine component. The method may be suitable for obtaining accurate and precise thermal image data associated with the plurality of cooling apertures having complex designs.

The main body and the seal of the apparatus may reduce or prevent formation of a cooling film (due to the flow of air) over a surface of the main body opposite to the seal. As a result, the thermal image data may include a segmented response from each cooling aperture. In other words, the thermal image data may include discrete data associated with each cooling aperture of the gas turbine engine component. Therefore, the inspection parameter determined by the method may be accurate.

In some embodiments, the inspection parameter being a blockage parameter.

In some embodiments, engaging the gas turbine engine component with the seal of the apparatus includes either retaining the main body in a fixed position and moving the gas turbine engine component towards the main body, such that the gas turbine engine component engages with the seal, or retaining the gas turbine engine component in a fixed position and moving the main body towards the gas turbine engine component, such that the gas turbine engine component engages with the seal.

In some embodiments, engaging the gas turbine engine component with the seal of the apparatus includes receiving and retaining the gas turbine engine component in an inspection fixture, and detachably coupling, via at least one pair of coupling elements, the main body with the inspection fixture, such that the gas turbine engine component engages with the seal.

Aspects and embodiments of the present disclosure will now be discussed with reference to the accompanying figures. Further aspects and embodiments will be apparent to those skilled in the art.

1 FIG. 10 10 12 10 14 15 14 12 12 14 15 12 12 10 shows a cross-sectional view of a portion of a gas turbine engine component. The gas turbine engine componentincludes a plurality of cooling apertures. The gas turbine engine componentincludes a first major surfaceand a second major surfacedisposed opposite to the first major surface. Each cooling aperturefrom the plurality of cooling aperturesmay extend from the first major surfaceto the second major surface. In other words, each cooling aperturemay be a through-aperture. The plurality of cooling aperturesmay have complex designs depending upon on desired application attributes of the gas turbine engine component.

15 10 15 10 12 18 10 12 18 16 15 10 18 1 FIG. 1 FIG. The second major surfacemay be a hot-side surface of the gas turbine engine component. Specifically, the second major surfacemay be exposed to a high temperature environment during use of the gas turbine engine component. The plurality of cooling aperturesmay be configured to direct a flow of air(depicted by arrows in) in order to provide thermal protection to the gas turbine engine component. In some cases, the plurality of cooling aperturesmay be configured to direct the airso as to form a cooling film(depicted by an arrow in) over the second major surfaceof the gas turbine engine component. The airmay correspond to a cooling fluid.

10 10 The gas turbine engine componentmay be a heatshield, a liner, and a tile of a combustor of the gas turbine engine. As another example, the gas turbine engine componentmay be turbine blade of the gas turbine engine.

2 FIG. 200 10 shows a cross-sectional view of a portion of a systemfor inspecting a gas turbine engine component (e.g., the gas turbine engine component) having a plurality of cooling apertures in accordance with an embodiment of the present disclosure.

200 100 100 110 122 12 10 122 122 110 110 112 114 112 122 112 114 The systemincludes an apparatus. The apparatusincludes a main bodyincluding a plurality of body aperturesconfigured to at least partially align with the plurality of cooling aperturesof the gas turbine engine component. Each body aperturefrom the plurality of body aperturesextends through the main body. Specifically, the main bodyincludes a first major body surfaceand a second major body surfacedisposed opposite to the first major body surface. Each body aperturemay extend from the first major body surfaceto the second major body surface.

110 126 122 126 112 114 126 126 122 122 126 The main bodyfurther includes a plurality of aperture wall surfacesdefining the plurality of body apertures. The plurality of aperture wall surfacesmay extend from the first major body surfaceto the second major body surface. Each aperture wall surfacefrom the plurality of aperture wall surfacesdefines a corresponding body aperturefrom the plurality of body apertures. Each aperture wall surfacemay be continuous and discrete.

100 160 110 160 110 160 10 160 10 160 10 160 110 10 160 110 160 10 The apparatusfurther includes a sealconnected or connectable to the main body. The sealmay be detachably connectable or permanently connectable to the main body. The sealis configured to engage with the gas turbine engine component. Specifically, the sealmay be configured to sealingly engage with the gas turbine engine component. The sealmay have a geometry and a curvature that matches with the gas turbine engine component. The sealand the main bodymay be designed to optimise sealing with the gas turbine engine component. For example, in some cases, the sealand the main bodymay be designed to provide adequate pressure across an interface between the sealand the gas turbine engine componentto optimise sealing.

160 166 122 166 166 160 160 162 164 162 166 162 164 The sealincludes a plurality of seal aperturescorresponding to the plurality of body apertures. Each seal aperturefrom the plurality of seal aperturesextends through the seal. Specifically, the sealincludes a first major seal surfaceand a second major seal surfacedisposed opposite to the first major seal surface. Each seal aperturemay extend from the first major seal surfaceto the second major seal surface.

166 122 110 166 122 The plurality of seal aperturesis at least partially aligned with the plurality of body aperturesof the main body, such that the plurality of seal aperturesis disposed or disposable in fluid communication with the plurality of body apertures.

100 10 100 12 10 100 10 12 The apparatusmay improve an inspection of the gas turbine engine component. Specifically, the apparatusmay facilitate obtaining accurate and precise data associated with the plurality of cooling aperturesof the gas turbine engine component. The apparatusmay be suitable for use with gas turbine engine components (such as the gas turbine engine component) having complex designs of the plurality of cooling apertures.

100 10 166 12 122 166 122 12 10 2 FIG. The apparatusmay be arranged in a testing configuration (as shown in) with respect to the gas turbine engine componentto carry out the inspection. In the testing configuration, the plurality of seal aperturesis at least partially aligned with the plurality of cooling apertures, and the plurality of body aperturesis at least partially aligned with the plurality of seal apertures, such that the plurality of body aperturesis disposed in fluid communication with the plurality of cooling aperturesof the gas turbine engine component.

110 160 12 110 160 114 12 100 12 10 The main bodyand the sealmay reduce or prevent formation of a cooling film (due to a flow of air directed through the plurality of cooling apertures) over a surface of the main bodyopposite to the seal(i.e., the second major body surface). As a result, a segmented response from each cooling aperturemay be obtained. In other words, the apparatusmay allow obtaining discrete data associated with each cooling apertureof the gas turbine engine component.

160 110 164 110 112 164 160 10 162 160 10 As discussed above, the sealis connected or connectable to the main body. The second major seal surfacemay be configured to engage with the main body. Further, the first major body surfacemay be configured to engage with the second major seal surface. Moreover, as discussed above, the sealis configured to engage with the gas turbine engine component. Specifically, the first major seal surfaceof the sealmay be configured to engage with the gas turbine engine component.

110 160 10 110 160 10 The main bodyand the sealmay be designed according to the gas turbine engine componentto be inspected. That is, the shape and size of each of the main bodyand the sealmay be dependent on the gas turbine engine component.

110 110 110 110 110 10 110 110 110 The main bodymay be made from any suitable material, such that the main bodyis capable of withstand clamping loads. As an example, the main bodymay be made from a metal, such as stainless steel. As another example, the main bodymay be made from a suitable stiff polymer. The main bodymay be designed to have a strength depending upon the size and shape of the gas turbine engine componentand inspection parameters. In some examples, the main bodymay have a low thermal effusivity. The thermal effusivity of the main bodymay be defined as the square root of the product of the thermal conductivity and the volumetric heat capacity of the main body.

160 160 12 166 10 12 160 160 160 162 164 160 160 The sealmay be made from any suitable material, such that the sealis rigid enough to prevent excessive deformation (which may result in misalignment of the plurality of cooling aperturesand the plurality of seal apertures, thereby resulting in undesired blockage), but flexible enough to adequately seal with the gas turbine engine componentto minimise leakage between the plurality of cooling apertures. As an example, the sealmay be made from a material having a suitable Shore A hardness. In some embodiments, the sealincludes a Shore A hardness from 40 to 60. In some embodiments, the Shore A hardness of the sealmay vary across its thickness (i.e., from the first major seal surfaceto the second major seal surface). This may improve the sealing performance of the seal. As another example, the sealmay be made from a rubber.

166 168 122 128 168 128 18 12 122 12 160 1 FIG. In some embodiments, each seal aperturehas a first diameter. Further, each body aperturehas a second diameter. The first diametermay be greater than the second diameter. This may facilitate passage of the air(shown in) from the plurality of cooling aperturesto the plurality of body apertures, thereby reducing undesired blockage of the plurality of cooling aperturesby the seal.

110 160 110 160 3 122 166 In some embodiments, the main bodyand the sealare integral. In some embodiments, the main bodyand the sealmay be integrally formed using an additive manufacturing method (e.g.,D printing). Use of additive manufacturing may allow creation of complex profiled designs and precise apertures (specifically, the plurality of body aperturesand the plurality of seal apertures).

160 110 110 110 160 160 110 In some other embodiments, the sealmay be separate from the main bodyand connected to the main bodyusing a suitable attachment method. For example, the main bodymay be made from stainless steel, the sealmay be made from a rubber, and the sealmay be bonded to the main body.

200 210 110 160 126 210 114 126 210 The systemfurther includes a thermography deviceconfigured to obtain thermal image data associated with a surface of the main bodyopposite to the sealand the plurality of aperture wall surfaces. Specifically, the thermography devicemay be configured to obtain the thermal image data associated with the second major body surfaceand the plurality of aperture wall surfaces. The thermography devicemay include, for example, a thermal imaging camera.

210 12 210 12 10 12 In the testing configuration, the thermal image data obtained by the thermography devicemay include a segmented response from each cooling aperture. In other words, the thermography devicemay capture discrete data associated with each cooling apertureof the gas turbine engine component. This may allow determining accurate inspection parameters associated the plurality of cooling apertures.

126 210 114 210 110 114 10 100 10 10 In some embodiments, each aperture wall surfacemay have a set of first predetermined infrared properties. For example, the set of first predetermined infrared properties may include a high infrared emissivity, a low infrared reflectivity, and a low infrared transmissivity. The set of first predetermined infrared properties (e.g., infrared emittance, infrared reflectance, and infrared transmittance) may be calibrated to improve thermographic inspection by the thermography device. Further, the second major body surfacemay have a set of second predetermined infrared properties different from the set of first predetermined infrared properties. The set of second predetermined infrared properties (e.g., infrared emittance, infrared reflectance, and infrared transmittance) may be calibrated to improve thermographic inspection by the thermography device. In some embodiments, the main bodymay further include a layer of a high emissivity paint or coating (not shown) disposed on the second major body surface. As compared to conventional techniques that include coating the gas turbine engine componentwith high emissivity paint, the apparatusmay eliminate the need to remove the high emissivity paint from the gas turbine engine componentafter inspection and before use of the gas turbine engine component.

110 132 134 132 132 114 122 136 138 136 134 138 134 138 138 210 In some embodiments, the main bodydefines a planeand a normalto the plane. In some embodiments, the planemay be defined by the second major body surface. The plurality of body aperturesmay include a set of first body aperturesand a set of second body apertures. The set of first body aperturesmay be aligned with the normal. The set of second body aperturesmay be obliquely inclined to the normal. At least some second body aperturesfrom the set of second body aperturesmay be configured to compensate for a parallax error of the thermography device.

3 3 FIGS.A andB 3 FIG.A 3 FIG.B 100 100 100 show perspective views of the apparatusin accordance with an embodiment of the present disclosure. Specifically,shows a bottom perspective view of the apparatus, andshows top perspective view the apparatus.

3 3 FIGS.A andB 3 FIG.A 110 142 144 142 122 142 110 115 142 112 115 10 160 115 Referring to, the main bodymay further include a central portionand a peripheral portionsurrounding the central portion. In some embodiments, the plurality of body aperturesmay be disposed on the central portion. As shown in, the main bodymay include a platformlocated on the central portionand partially forming the first major body surface. The platformmay be shaped or contoured based on the gas turbine engine component. Further, the sealmay be connectable or connected to the platform.

110 146 144 146 146 144 142 146 146 110 146 112 114 The main bodymay further include at least one pair of coupling aperturesspaced apart from each other and disposed on the peripheral portion. Each pair of coupling aperturesfrom the at least one pair of coupling aperturesmay be disposed on the peripheral portion, such that the central portionis disposed between the pair of coupling apertures. Each of the at least one pair of coupling aperturesextends through the main body. Specifically, each of the at least one pair of coupling aperturesmay extend from the first major body surfaceto the second major body surface.

4 FIG. 100 shows an exploded perspective view of the apparatusin accordance with an embodiment of the present disclosure.

100 180 180 182 10 182 10 180 184 182 180 186 146 110 186 184 The apparatusmay further include an inspection fixture. The inspection fixturemay include a receiving portionconfigured to receive and retain the gas turbine engine component. The receiving portionmay be shaped based on the gas turbine engine component. The inspection fixturemay further include a coupling portionsurrounding the receiving portion. The inspection fixturemay further include at least one pair of coupling featurescorresponding to the at least one pair of coupling aperturesof the main body. The at least one pair of coupling featuresis disposed on the coupling portion.

110 180 186 100 148 146 186 110 180 148 186 110 180 110 180 The main bodymay be detachably connected to the inspection fixturevia the at least one pair of coupling features. Specifically, the apparatusmay further include at least one pair of coupling elementsconfigured to extend through the at least one pair of coupling aperturesand detachably couple with the at least one pair of coupling featuresto detachably couple the main bodywith the inspection fixture. The at least one pair of coupling elementsmay include, for example, bolts, and the at least one pair of coupling featuresmay include, for example, nuts. It may be noted that various other techniques may be employed to detachably couple the main bodywith the inspection fixture. For example, the main bodymay be detachably coupled with the inspection fixturevia snap-fit features, and other fastening methods.

10 182 180 110 180 146 110 186 180 148 146 186 210 114 110 126 10 In use, the gas turbine engine componentmay be positioned and retained in the receiving portionof the inspection fixture. Subsequently, the main bodymay be positioned on the inspection fixture, such that the at least one pair of coupling aperturesof the main bodyat least partially align with the at least one at least one pair of coupling featuresof the inspection fixture. Then, the at least one pair of coupling elementsmay be inserted through the at least one pair of coupling aperturesand detachably coupled with the at least one pair of coupling features. Subsequently, the thermography devicemay be used to obtain the thermal image data associated with the second major body surfaceof the main bodyand the plurality of aperture wall surfacesto inspect the gas turbine engine component.

5 FIG.A 2 FIG. 210 10 shows a schematic thermogram obtained by the thermography device(shown in) during inspection of the gas turbine engine component.

12 10 15 10 12 12 12 5 FIG.A When air was directed through the plurality of cooling aperturesof the gas turbine engine component, a cooling film was formed over the second major surfaceof the gas turbine engine component. As can be seen in, the cooling film filled areas between adjacent cooling aperturesfrom the plurality of cooling apertures, thereby preventing accurate and/or precise inspection of the plurality of cooling apertures.

5 FIG.B 2 FIG. 10 210 100 shows a schematic thermogram of the gas turbine engine componentobtained by the thermography device(shown in) using the apparatus.

2 5 FIGS.andB 100 10 12 10 122 110 100 160 110 114 110 12 210 Referring to, when the apparatuswas used for inspection of the gas turbine engine component, air that was directed through the plurality of cooling aperturesof the gas turbine engine componentemanated through the plurality of body aperturesof the main body. The apparatus, or more specifically, the sealand the main bodyreduced formation of a cooling film over the second major body surfaceof the main body. As a result, a segmented response from each cooling aperturewas obtained by the thermography device.

6 FIG. 1 FIG. 300 10 shows a flowchart depicting various steps of a methodof inspecting a gas turbine engine component (e.g., the gas turbine engine componentof) having a plurality of cooling apertures in accordance with an embodiment of the present disclosure.

310 300 300 10 1 FIG. At step, the methodincludes providing a gas turbine engine component including a plurality of cooling apertures. Referring to, for example, the methodmay include providing the gas turbine engine component.

320 300 300 100 2 FIG. At step, the methodfurther includes providing an apparatus. The apparatus includes a main body including a plurality of body apertures configured to at least partially align with the plurality of cooling apertures of the gas turbine engine component. Each body aperture from the plurality of body apertures extends through the main body. The main body further includes a plurality of aperture wall surfaces defining the plurality of body apertures. Each aperture wall surface from the plurality of aperture wall surfaces defines a corresponding body aperture from the plurality of body apertures. The apparatus further includes a seal including a plurality of seal apertures corresponding to the plurality of body apertures. Each seal aperture from the plurality of seal apertures extends through the seal. The plurality of seal apertures is at least partially aligned with the plurality of body apertures of the main body. Referring to, for example, the methodmay include providing the apparatus.

330 300 300 160 110 166 122 160 110 2 FIG. At step, the methodfurther includes connecting the seal to the main body, such that the plurality of seal apertures is disposed in fluid communication with the plurality of body apertures. Referring to, for example, the methodmay include connecting the sealto the main body, such that the plurality of seal aperturesis disposed in fluid communication with the plurality of body apertures. Any suitable method may be employed to connect the sealto the main body.

340 300 300 10 160 100 12 166 2 FIG. At step, the methodfurther includes engaging the gas turbine engine component with the seal of the apparatus, such that the plurality of cooling apertures aligns with the plurality of seal apertures. Referring to, for example, the methodmay include engaging the gas turbine engine componentwith the sealof the apparatus, such that the plurality of cooling aperturesaligns with the plurality of seal apertures.

In some embodiments, engaging the gas turbine engine component with the seal of the apparatus may include either retaining the main body in a fixed position and moving the gas turbine engine component towards the main body, such that the gas turbine engine component engages with the seal, or retaining the gas turbine engine component in a fixed position and moving the main body towards the gas turbine engine component, such that the gas turbine engine component engages with the seal.

2 FIG. 10 160 100 110 10 110 10 160 10 160 100 10 110 10 10 160 110 10 Referring to, for example, engaging the gas turbine engine componentwith the sealof the apparatusmay include retaining the main bodyin a fixed position and moving the gas turbine engine componenttowards the main body, such that the gas turbine engine componentengages with the seal. In another example, engaging the gas turbine engine componentwith the sealof the apparatusmay include retaining the gas turbine engine componentin a fixed position and moving the main bodytowards the gas turbine engine component, such that the gas turbine engine componentengages with the seal. Any suitable retaining mechanism may be used to retain the main bodyand/or the gas turbine engine componentin a fixed position.

4 FIG. 10 160 100 10 180 148 110 180 10 160 In some embodiments, engaging the gas turbine engine component with the seal of the apparatus includes receiving and retaining the gas turbine engine component in an inspection fixture and detachably coupling, via at least one pair of coupling elements, the main body with the inspection fixture, such that the gas turbine engine component engages with the seal. Referring to, for example, engaging the gas turbine engine componentwith the sealof the apparatusmay include receiving and retaining the gas turbine engine componentin the inspection fixtureand detachably coupling, via the at least one pair of coupling elements, the main bodywith the inspection fixture, such that the gas turbine engine componentengages with the seal.

350 300 300 18 12 1 FIG. At step, the methodfurther includes directing a flow of air through the plurality of cooling apertures. Referring to, for example, the methodmay include directing the flow of airthrough the plurality of cooling apertures.

360 300 300 110 160 126 300 114 110 126 210 2 5 FIGS.andB At step, the methodfurther includes obtaining thermal image data associated with a surface of the main body opposite to the seal and the plurality of aperture wall surfaces. Referring to, for example, the methodmay further include obtaining thermal image data associated with the surface of the main bodyopposite to the sealand the plurality of aperture wall surfaces. Specifically, the methodmay include obtaining the thermal image data associated with the second major body surfaceof the main bodyand the plurality of aperture wall surfacesusing the thermography device.

370 300 At step, the methodfurther includes determining an inspection parameter associated with the plurality of cooling apertures based on the thermal image data. The inspection parameter may include any parameter associated with the plurality of cooling apertures.

12 10 In some embodiments, the inspection parameter includes a blockage parameter. The blockage parameter may be indicative of which of the plurality of cooling aperturesof the gas turbine engine componentare blocked, i.e., block flow of air therethrough.

The apparatus, system, and method of the present disclosure may improve an inspection of the gas turbine engine component. Specifically, the apparatus, system, and method may facilitate obtaining accurate and precise data associated with the plurality of cooling apertures of the gas turbine engine component.

Various examples have been described, each of which comprise various combinations of features. It will be appreciated by those skilled in the art that, except where clearly mutually exclusive, any of the features may be employed separately or in combination with any other features and the invention extends to and includes all combinations and sub-combinations of one or more features described herein.